54 Airworthiness Directives: 39 airplane, 8 rotorcraft, 5 engine, 1 propeller, 1 appliance.
AD 2001-24-09 · published Dec 3, 2001, effective Jan 7, 2002
Short Brothers Model SD3 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Short Brothers Model SD3 series airplanes, that requires repetitive tests (checks) of the engine power lever to ensure that the fuel control unit (FCU) lever is contacting the maximum stop, adjustment of the FCU rigging, if necessary, and an engine ground run for correct gas generator rotational speed. This AD also requires a static reduced power check on each engine to ensure correct operation of the reserve takeoff power (RTOP) system; and follow-on actions, if necessary. This action is necessary to prevent failure of the engines to reach adequate RTOP boost during takeoff, which could result in reduced controllability of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-23-51 · published Dec 5, 2001, effective Dec 10, 2001
Airbus Model A300 B4-600, B4-600R, and F4-600R (Collectively Called A300-600) Series Airplanes; and Model A310 Series Airplanes
This document publishes in the Federal Register an amendment adopting airworthiness directive (AD) 2001-23-51 that was sent previously to all known U.S. owners and operators of certain Airbus Model A300 B4-600, B4-600R, and F4-600R (collectively called A300-600) series airplanes; and Model A310 series airplanes by individual notices. This AD requires a one-time detailed visual inspection to detect repairs and alterations to, and damage of the vertical stabilizer attachment fittings, including the main attachment lugs and the transverse (side) load fittings; and the rudder hinge fittings, hinge arms, and support fittings for all rudder hinges, and rudder actuator support fittings; and repair, if necessary. This AD also requires that operators report results of inspection findings to the FAA. This action is prompted by an airplane accident shortly after takeoff from John F. Kennedy International Airport, Jamaica, New York. The actions specified by this AD are intended to prevent failure of the vertical stabilizer-to-fuselage attachment fittings or transverse (side) load fittings, or rudder-to-vertical stabilizer attachment fittings, which could result in loss of the vertical stabilizer and/or rudder and consequent loss of control of the airplane.
AD 2001-24-10 · published Dec 5, 2001, effective Dec 20, 2001
Fokker Model F.28 Mark 0100 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Fokker Model F.28 Mark 0100 series airplanes. This action requires repetitive inspections of certain main landing gear (MLG) main fittings to detect forging defects, and rework of the main fittings if necessary. This action is necessary to detect forging defects of the MLG main fittings, which could lead to cracking and result in significant structural damage to the airplane and possible injury to the occupants.
AD 2001-25-01 · published Dec 5, 2001, effective Dec 20, 2001
McDonnell Douglas Model DC-8-33, -43, -51, -52, -53, and -55 Series Airplanes; Model DC-8F-54, and -55 Series Airplanes; and Model DC-8-61, -61F, -62, -62F, -63, -63F, -71, -71F, -72, -72F, -73, and -73F Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain McDonnell Douglas Model DC-8-33, -43, -51, - 52, -53, and -55 series airplanes; Model DC-8F-54, and -55 series airplanes; and Model DC-8-61, -61F, -62, -62F, -63, -63F, -71, -71F, - 72, -72F, -73, and -73F series airplanes. This action requires repetitive inspections of the electrical connectors of the explosive cartridge wiring of the engine fire extinguisher containers to verify if the identification number labels are installed and legible; repetitive electrical tests of all explosive cartridge wiring of the engine fire extinguisher containers to verify proper installation and function; and corrective actions, if necessary. This action is necessary to detect and correct cross-wired electrical connectors of the fire extinguishing system, which could release fire extinguishing agent into the incorrect engine nacelle in the event of an engine fire.
AD 2001-24-11 · published Dec 6, 2001, effective Dec 11, 2001
Raytheon Model Beech 400, 400A, and 400T Series Airplanes, Model Mitsubishi MU-300 Airplanes, and Model Beech MU-300-10 Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to all Raytheon Model Beech 400, 400A, and 400T series airplanes, Model Mitsubishi MU-300 airplanes, and Model Beech MU-300-10 airplanes. This action requires revising the Emergency Procedures Section of the Airplane Flight Manual to ensure the flightcrew is advised of in-flight procedures in the event of loss of airspeed indication. Such loss of airspeed indication and the resulting adverse effects on certain connecting systems could result in reduced controllability of the airplane.
AD 2001-25-03 · published Dec 11, 2001, effective Dec 17, 2001
Cirrus Design Corporation Models SR20 and SR22 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to certain Cirrus Design Corporation (CDC) Models SR20 and SR22 airplanes. This AD requires you to inspect one time for understrength rivets on the elevator torque tube and rudder hinge and replace any understrength rivets. This AD is the result of CDC notifying FAA that understrength rivets were mixed in production supplies. The actions specified by this AD are intended to detect and replace understrength rivets in the elevator and rudder, which could result in failure of the control surfaces. Such failure could lead to a loss of control of the airplane in flight.
AD 2001-24-13 · published Dec 12, 2001, effective Jan 16, 2002
McDonnell Douglas Model DC-9-10, -20, -30, and -40 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, and - 40 series airplanes, that requires rework and reidentification of certain reflector assemblies of the passenger ceiling lights; and installation of a support channel above the reflector, as applicable. This amendment is prompted by reports of heat damaged lamp reflectors and scorched insulation blankets in the main cabin due to the lamps inside the reflectors creating high temperatures. The actions specified by this AD are intended to prevent overheating of the lamp reflectors, which could result in smoke and fire in the main cabin.
AD 2001-24-14 · published Dec 12, 2001, effective Jan 16, 2002
McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 Series Airplanes; C-9 Airplanes; and Model DC-9-81, -82, -83, and -87 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes; C-9 airplanes; and Model DC-9-81, -82, -83, and -87 series airplanes, that requires an inspection of the power feeder bus cables of the auxiliary power unit (APU) for overheat damage between certain fuselage stations; and corrective action(s), if necessary. This action is necessary to prevent loose terminal stud connections and consequent damage to the small copper terminals, which could result in overheating of the wires at the terminal strip. Such overheating could cause an electrical failure and could result in smoke and fire in the electrical/electronic compartment. This action is intended to address the identified unsafe condition.
AD 2001-24-15 · published Dec 12, 2001, effective Jan 16, 2002
McDonnell Douglas Model DC-9-10, -30, and -40 Series Airplanes and C-9 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -30, and -40 series airplanes and C-9 airplanes, that requires an inspection to detect chafing of the wiring of the attendants' work light of the aft cabin, and repair of chafed wiring. This AD also requires modification and reidentification of the attendants' work light assemblies of the aft cabin. This action is necessary to prevent chafing of the ground wire against the positive contact of the lamp of the attendants' work light of the aft cabin, and consequent arcing or arcing damage to the wiring of the attendants' work light and transformer of the aft cabin. Such arcing or arcing damage could result in short circuits and consequent smoke and fire in the aft cabin area. This action is intended to address the identified unsafe condition.
AD 2001-24-16 · published Dec 12, 2001, effective Jan 16, 2002
McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 Series Airplanes and C-9 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes and C-9 airplanes. This AD requires an inspection to detect chafing or damage at the conduit and support bracket interface in the forward electrical power center (EPC); and repair or replacement of wires with new wires, if necessary. For certain airplanes, this AD also requires installation of grommets on the conduits of the forward EPC. These actions are necessary to prevent chafing of electrical cables in the forward EPC and a possible short within a conduit, which could result in smoke and fire in the cockpit. These actions are intended to address the identified unsafe condition.
AD 2001-24-17 · published Dec 12, 2001, effective Jan 16, 2002
McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 Series Airplanes; C-9 Airplanes; and Model DC-9-81, -82, and -83 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes; C-9 airplanes; and Model DC-9-81, -82, and - 83 series airplanes. This AD requires modification of the light switch for the cargo compartment(s). This action is necessary to prevent generation of smoke and fire in a cargo compartment due to an illuminated light with a missing cover contacting cargo contents for an extended period of time. This action is intended to address the identified unsafe condition.
AD 2001-24-18 · published Dec 12, 2001, effective Jan 16, 2002
McDonnell Douglas Model DC-9-10, -30, and -40 Series Airplanes and C-9 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -30, and -40 series airplanes and C-9 airplanes, that requires revising the wiring of the sidewall lights in the forward and aft passenger compartment. The actions specified by this AD are intended to prevent the control switch of the cabin sidewall lights on the forward attendant's panel from overheating, which could result in shorting of the dim, bright, and power terminals, and consequent smoke/fire in the passenger compartment. This action is intended to address the identified unsafe condition.
AD 2001-24-19 · published Dec 12, 2001, effective Jan 16, 2002
McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 Series Airplanes; C-9 Airplanes; Model DC-9-81, -82, -83, and -87 Series Airplanes; and Model MD-88 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes; C-9 airplanes; Model DC-9-81, -82, -83, and - 87 series airplanes; and Model MD-88 airplanes, that requires an inspection to detect chafing or overheat damage of the electrical wires located at fuselage station Y=110.000 bulkhead of the lower nose left tunnel; and corrective actions, if necessary. This AD also requires replacing the external power ground stud with a new ground stud using new attaching parts, torquing new attachments, and installing a nameplate. This action is necessary to prevent loose external power ground wires, which could cause arcing and overheated wire insulation and consequent smoke/fire in the cockpit. This action is intended to address the identified unsafe condition.
AD 2001-24-20 · published Dec 12, 2001, effective Jan 16, 2002
McDonnell Douglas Model DC-10-10, -15, -30, -30F (KC-10A and KDC-10 Military), and -40 Series Airplanes; and Model MD-10-10F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -15, -30, -30F (KC-10A and KDC-10 military), and -40 series airplanes; and Model MD- 10-10F series airplanes, that requires an inspection to verify that the wire connections at circuit breakers are properly connected, and correction of any incorrect wire connection at the circuit breakers. This amendment is necessary to prevent loss of protection by the circuit breakers in the flight engineer's equipment panel due to improperly wired connections at the circuit breakers, which could result in wire damage and could lead to smoke and/or fire in the cockpit. This action is intended to address the identified unsafe condition.
AD 2001-24-21 · published Dec 12, 2001, effective Jan 16, 2002
McDonnell Douglas Model DC-10 Series Airplanes, and Model MD-10-10F and -30F Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-10 series airplanes, that currently requires a one-time detailed visual inspection to determine if wire segments of the wire bundle routed through the feed through on the aft side of the flight engineer's station are damaged or chafed, and corrective actions, if necessary. This amendment also requires revising the wire bundle support clamp installation at the flight engineer's station. This action is necessary to prevent chafing of the wire bundle located behind the flight engineer's panel caused by the wire bundle coming in contact with the lower edge of the feed through and consequent electrical arcing, which could result in smoke and fire in the cockpit. This action is intended to address the identified unsafe condition.
AD 2001-24-22 · published Dec 12, 2001, effective Jan 16, 2002
McDonnell Douglas Model DC-10-10, -10F, -30, -30F (KC-10A and KDC-10), -40, and -40F Series Airplanes; and Model MD-10-10F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -10F, -30, -30F (KC-10A and KDC-10), -40, and -40F series airplanes; and Model MD-10- 10F series airplanes. This AD requires an inspection of the power feeder cable assembly of the auxiliary power unit (APU) for chafing, correct type of clamps, and proper clamp installation; and corrective actions, if necessary. The actions specified by this AD are intended to prevent loss of the APU generator due to chafing of the generator power feeder cables, and consequent electrical arcing and smoke/fire in the APU compartment. This action is intended to address the identified unsafe condition.
AD 2001-24-23 · published Dec 12, 2001, effective Jan 16, 2002
McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F (KC-10A and KDC-10), -40, and -40F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-10-10, -10F, -15, -30, -30F (KC-10A and KDC-10), -40, and -40F series airplanes, that requires modification of the battery ground cable installation in the center accessory compartment (CAC). The actions specified by this AD are intended to prevent a loose ground stud and/or cable attachments, and consequent chafing of adjacent structure and electrical arcing, which could result in smoke/fire in the CAC in the event of fuel leakage. This action is intended to address the identified unsafe condition.
AD 2001-24-24 · published Dec 12, 2001, effective Jan 16, 2002
McDonnell Douglas Model DC-9-10 and -30 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10 and -30 series airplanes, that requires an inspection of the power feeder cable for evidence of chafing, and repair of any chafed power feeder cable. This amendment also requires replacement of the wiring support clip (standoff) of the power feeder cable with a new, improved wiring support clip. This action is necessary to prevent chafing and arcing of the power feeder cable and adjacent airplane structure and system components, and consequent smoke/fire in an engine nacelle. This action is intended to address the identified unsafe condition.
AD 2001-24-25 · published Dec 12, 2001, effective Jan 16, 2002
McDonnell Douglas Model DC-9-10, -20, -30, and -40 Series Airplanes and C-9 Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, and - 40 series airplanes and C-9 airplanes. This amendment requires modification of the spoiler control system, and installation of protective interlock box assemblies in the spoiler circuit. This amendment is necessary to prevent smoke/fire in the flight compartment in the event that the automatic spoiler actuator overheats, and/or loss of the spoiler control system, which could significantly reduce the braking effectiveness of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-24-26 · published Dec 12, 2001, effective Jan 16, 2002
Airbus Model A300 B2 and B4, A300 B4-600 and B4-600R, and A310 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Airbus Model A300 B2 and B4, A300 B4-600 and B4- 600R, and A310 series airplanes, that requires modification of the terminal blocks of the starter feeder line of the auxiliary power unit (APU). This action is necessary to prevent slackness and subsequent overheat and arcing of certain wiring connections. This action is intended to address the identified unsafe condition.
AD 2001-24-27 · published Dec 12, 2001, effective Jan 16, 2002
McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 Series Airplanes; Model DC-9-81, -82, -83, and -87 Series Airplanes; Model MD-88 Airplanes; and C-9 Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-9-10, -20, -30, -40, and -50 series airplanes; Model DC-9-81, -82, -83, and -87 series airplanes; Model MD-88 airplanes; and C-9 airplanes, that currently requires repetitive inspections to detect cracking of the rudder pedal adjuster hub assembly, and replacement of the assembly, if necessary. That AD also provides for an optional terminating action for the repetitive inspections. This amendment requires accomplishment of a new terminating action for the repetitive inspections. This amendment is prompted by that FAA's determination that further rulemaking is necessary. The actions specified by this AD are intended to prevent loss of rudder pedal control and reduction of braking capability.
AD 2001-24-28 · published Dec 12, 2001, effective Jan 16, 2002
McDonnell Douglas Model DC-8 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes, that currently requires repetitive visual and eddy current inspections to detect cracking of the rudder pedals adjuster hub assembly, and replacement of the assembly with a new assembly, if necessary. This amendment requires accomplishment of a terminating action for the repetitive inspections. This amendment also adds airplanes to the applicability of the existing AD. This amendment is prompted by the FAA's determination that further rulemaking is necessary. The actions specified by this AD are intended to prevent loss of rudder pedals control and reduction of braking capability.
AD 2001-24-29 · published Dec 12, 2001, effective Jan 16, 2002
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires a one-time inspection for chafing between the hose for the passenger oxygen system (hereinafter called the "oxygen hose") and adjacent electrical wire bundles at certain passenger service units, and corrective actions, if necessary. This AD also requires rerouting or reorienting the oxygen hose to ensure sufficient clearance between the hose and electrical wire bundles. This action is necessary to prevent chafing between the oxygen hose and adjacent electrical wire bundles, which could result in arcing of a chafed electrical wire bundle and consequent burn-through of the oxygen hose. If this occurs when the oxygen system is pressurized, such arcing could represent a potential ignition source in an oxygen-enriched environment. This action is intended to address the identified unsafe condition.
AD 2001-24-30 · published Dec 12, 2001, effective Jan 16, 2002
Boeing Model 747-200C and -200F Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-200C and -200F series airplanes, that requires installation of drip shields over certain shelves in the main equipment bay. This action is necessary to prevent water from dripping through floor panels of the main deck cargo bay onto wire bundles and electronic components, which could lead to the loss of function of multiple electronic components and, consequently, could reduce the flight crew's ability to operate in adverse conditions. This action is intended to address the identified unsafe condition.
AD 2001-24-31 · published Dec 12, 2001, effective Jan 16, 2002
Boeing Model 747 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747 series airplanes, that requires performing a one-time inspection for chafing of certain electrical wire bundles behind the flight engineer's panel in the cockpit; repairing any chafed wire bundles, if necessary; and installing Teflon sleeving over the inspected wire bundles and rerouting them. This action is necessary to prevent burning of electrical wires, which could result in smoke in the cockpit and loss of function of several airplane systems. This action is intended to address the identified unsafe condition.
AD 2001-24-32 · published Dec 12, 2001, effective Jan 16, 2002
Boeing Model 747-100, 747-200B, 747-200C, 747-200F, 747SP, and 747SR Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 747-100, 747-200B, 747-200C, 747- 200F, 747SP, and 747SR series airplanes. This AD requires a one-time inspection for chafing of certain wire bundles behind the flight engineer's panel; repairs, if necessary; and a modification to reroute a certain electrical wire bundle to ensure sufficient clearance between that wire bundle and an adjacent flood light support bracket. This action is necessary to prevent chafing of certain electrical wire bundles, which could result in smoke in the cockpit, and uncommanded discharge of fire extinguishing bottles for the No. 4 engine and consequent reduction of the ability to fight a fire in the No. 4 engine. This action is intended to address the identified unsafe condition.
AD 2001-24-33 · published Dec 12, 2001, effective Jan 16, 2002
Boeing Model 737-100, -200, and -200C Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 737-100, -200, and -200C series airplanes, that requires a one-time inspection for damage (i.e., chafing) of the power feeder wire bundle for the auxiliary power unit (APU) generator and the first officer's elevator down control cable and for proper separation between that wire bundle and control cable, and corrective action, if necessary. For certain airplanes, this amendment also requires attaching the power feeder wire bundle to adjacent wire bundles. This action is necessary to prevent a short circuit and resultant arcing between the wire bundle and control cable, which could sever the control cable. Failure of the first officer's elevator down control cable, if combined with a subsequent failure of the captain's elevator down control cable, could result in loss of elevator control of the airplane. This action is intended to address the identified unsafe condition.
AD 2001-24-34 · published Dec 12, 2001, effective Jan 16, 2002
McDonnell Douglas Model DC-8-70 Series Airplanes
This amendment supersedes an existing airworthiness directive (AD), applicable to all McDonnell Douglas Model DC-8-70 series airplanes, that currently requires repetitive inspections and repair or replacement, if necessary, of the generator power feeder cables, supporting brackets, and clamps at all the engine pylons. This amendment requires accomplishment of a terminating action for the repetitive inspections. This amendment also requires replacement of the support clamps of the generator power feeder cable on engine nacelles/ pylons 1, 2, 3, and 4 with new support clamps. This amendment is prompted by the FAA's determination that further rulemaking is necessary. The actions specified by this AD are intended to prevent a fire on the ground if a fuel leak exists in an engine pylon.
AD 2001-22-09 · published Dec 14, 2001, effective Dec 4, 2001
Bombardier Model CL-600-2B19 Series Airplanes
This document corrects information in an existing airworthiness directive (AD) that applies to certain Bombardier Model CL-600-2B19 series airplanes. That AD currently requires repetitive eddy current inspections for cracking of the main landing gear (MLG) main fittings, and replacement with a new or serviceable MLG, if necessary. That AD also requires servicing the MLG shock struts; inspecting the MLG shock struts for nitrogen pressure, visible chrome dimension, and oil leakage; and performing corrective actions, if necessary. This document corrects an error that resulted in the omission of the AD and amendment numbers in the "Product Identification" section of the AD. This correction is necessary to ensure that the correct AD and amendment numbers are specified.
AD 2001-25-10 · published Dec 21, 2001, effective Jan 25, 2002
Pilatus Aircraft Ltd. Models PC-12 and PC-12/45 Airplanes
This amendment adopts a new airworthiness directive (AD) that supersedes Airworthiness Directive (AD) 99-19-32, which applies to certain Pilatus Aircraft Ltd. (Pilatus) Models PC-12 and PC-12/45 airplanes. AD 99-19-32 currently requires you to inspect the flap actuator internal gear system for correct end-play and backlash measurements and accomplish any corrective adjustments, as necessary. Pilatus has identified modifications for the flap system and designed and manufactured a new flap control and warning unit (FCWU) that permits the flap power drive-unit circuit breaker to close during flight. This AD requires you to modify the flap control wiring and install a flap power drive-unit field control panel. The actions specified by this AD are intended to allow the flap power drive-unit circuit breaker to close during flight and prevent current surges in the flap control system. If the pilot cannot close the circuit breaker during flight, the flight control and warning unit (FCWU) would not sense a worn actuator. Current surges in the flap control system could decrease the electrical life of the flap power drive-unit motor contactor. Both conditions have the potential for flap system failure with consequent reduced or loss of control of the airplane.
AD 2001-26-01 · published Dec 26, 2001, effective Jan 30, 2002
McDonnell Douglas Model DC-8 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes that have been converted from a passenger-to a cargo-carrying ("freighter") configuration. This amendment requires, among other actions, modification of the main deck cargo door structure and fuselage structure; modification of a main deck cargo door hinge; modification of the main deck cargo floor; and installation of a main deck cargo 9g crash barrier; as applicable. The actions specified by this AD are intended to prevent opening of the cargo door while the airplane is in flight or collapse of the main deck cargo floor, and consequent rapid decompression of the airplane including possible loss of flight control or severe structural damage. These actions are intended to address the identified unsafe condition.
AD 2001-26-02 · published Dec 26, 2001, effective Jan 30, 2002
McDonnell Douglas Model DC-8 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes that have been converted from a passenger-to a cargo-carrying ("freighter") configuration. This amendment requires, among other actions, modification of the main deck cargo door structure and fuselage structure; modification of the main deck cargo floor; and installation of a main deck cargo 9g crash barrier; as applicable. These actions are necessary to prevent opening of the cargo door while the airplane is in flight or collapse of the main deck cargo floor, and consequent rapid decompression of the airplane including possible loss of flight control or severe structural damage. These actions are intended to address the identified unsafe condition.
AD 2001-26-03 · published Dec 26, 2001, effective Jan 30, 2002
McDonnell Douglas Model DC-8 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes that have been converted from a passenger- to a cargo-carrying ("freighter") configuration. This amendment requires, among other actions, modification of the main deck cargo door structure and fuselage structure; modification of a main deck cargo door hinge; modification of the main deck cargo floor; and installation of a main deck cargo 9g crash barrier. These actions are necessary to prevent opening of the cargo door while the airplane is in flight or collapse of the main deck cargo floor, and consequent rapid decompression of the airplane including possible loss of flight control or severe structural damage. These actions are intended to address the identified unsafe condition.
AD 2001-26-04 · published Dec 26, 2001, effective Jan 30, 2002
McDonnell Douglas Model DC-8 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain McDonnell Douglas Model DC-8 series airplanes that have been converted from a passenger-to a cargo-carrying ("freighter") configuration, that requires, among other actions, modification of the main deck cargo door structure and fuselage structure; replacement of fasteners in the two door-side hinge elements; modification of the main deck cargo floor; and installation of a main deck cargo 9g crash barrier. The actions specified by this AD are intended to prevent opening of the cargo door while the airplane is in flight, and consequent rapid decompression of the airplane including possible loss of flight control or severe structural damage. These actions are intended to address the identified unsafe condition.
AD 2001-25-09 · published Dec 27, 2001, effective Jan 18, 2002
Dornier Luftfahrt GmbH Model 228-212 Airplanes
This amendment adopts a new airworthiness directive (AD) that applies to all Dornier Luftfahrt GmbH (Dornier) Model 228-212 airplanes that have a certain brake assembly installed. This AD requires you to inspect the brake housing subassembly for cracks, nicks, or corrosion (referred to as damage). This AD also requires you to replace damaged brake housing assemblies and modify the torque take-out cavity. This AD is the result of mandatory continuing airworthiness information (MCAI) issued by the airworthiness authority for Germany. The actions specified by this AD are intended to detect and correct damage to the brake housing assembly, which could result in failure of this assembly. Such failure could lead to loss of braking action on landing and possible loss of control of the airplane.
AD 2001-26-07 · published Dec 27, 2001, effective Jan 11, 2002
Gulfstream Model G-IV Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Gulfstream Model G-IV series airplanes. This action requires an inspection of the electrical connections for the fire extinguisher bottles; an inspection after any subsequent maintenance affecting the fire extinguisher bottles; and corrective action, if necessary. This action is prompted by a report indicating that the electrical connections for the fire extinguisher bottle squibs had been improperly installed either during manufacturing or during subsequent maintenance. This action is necessary to prevent fire extinguishing agent from being discharged into the wrong location, which could result in failure to extinguish an in-flight fire on an affected engine and jeopardize operation of the opposite engine.
AD 2001-26-08 · published Dec 27, 2001, effective Jan 31, 2002
Airbus Model A300 B2 Series Airplanes and Model A300 B4-2C, B4-103, and B4-203 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to all Airbus Model A300 B2 series airplanes and Model A300 B4-2C, B4-103, and B4-203 series airplanes, that requires identifying the types and areas of repairs on the airplane between frame 10 and frame 80, and performing follow-on actions for certain repairs. These actions are necessary to detect and correct fatigue cracking of certain repairs of the fuselage between frame 10 and frame 80, which could result in reduced structural integrity of the airplane. These actions are intended to address the identified unsafe condition.
AD 2001-26-09 · published Dec 27, 2001, effective Jan 31, 2002
Boeing Model 767-200 Series Airplanes
This amendment adopts a new airworthiness directive (AD), applicable to certain Boeing Model 767- 200 series airplanes, that requires a one-time inspection of the water line heater tape where it passes close to the duct assemblies of the air distribution system for the flight compartment to detect damage, and follow-on actions. This amendment also requires eventual replacement of certain duct assemblies or foam insulation on those duct assemblies with new duct assemblies or improved foam insulation. This action is necessary to prevent ignition of foam insulation on the air distribution ducts, which could result in a fire in the airplane. This action is intended to address the identified unsafe condition.
AD 2001-26-10 · published Dec 27, 2001, effective Jan 11, 2002
Airbus Model A319, A320, and A321 Series Airplanes
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Airbus Model A319, A320, and A321 series airplanes. This action requires an in-situ one-time detailed visual inspection of Draeger Type I oxygen containers, located in the passenger service units, and Draeger Type II oxygen containers, located in the utility areas, for the presence of foam pads. This action also requires the installation of a new foam pad, if necessary; and other actions to ensure proper operations of the masks. This action is necessary to prevent failure of the oxygen containers to deliver oxygen to the passengers in the event of a rapid decompression or cabin depressurization. This action is intended to address the identified unsafe condition.
AD 2001-24-07 · published Dec 3, 2001, effective Jan 7, 2002
Agusta S.p.A. Model A109C, A109E, and A109K2 Helicopters
This amendment supersedes an existing airworthiness directive (AD) that applies to Agusta S.p.A. (Agusta) Model A109C, A109E, and A109K2 helicopters and currently requires inspecting the main rotor blade (blade) tip cap for bonding separation and a crack. This amendment contains the same requirements as the existing AD but also requires a tap inspection of the tip cap for bonding separation in the blade bond area and a dye penetrant inspection of the tip cap leading edge along the welded joint line of the upper and lower tip cap skin shells for a crack. This amendment is prompted by three occurrences in which the blade tip cap leading edge opened in flight due to cracks, resulting in excessive helicopter vibration. The actions specified by this AD are intended to prevent failure of a blade tip cap, excessive vibration, and subsequent loss of control of the helicopter.
AD 2001-24-08 · published Dec 3, 2001, effective Jan 7, 2002
Eurocopter France Model EC 120 Helicopters
This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter France (ECF) Model EC120B helicopters and currently requires adjusting the clearance of the cabin sliding door if necessary. This amendment requires adding an end stop to the front rail and modifying the rear stop of the middle rail to increase its adjustment range for certain cabin sliding doors. This amendment is prompted by an in-flight loss of a cabin sliding door, which had been locked in the open position. The actions specified by this AD are intended to prevent in-flight loss of a cabin sliding door, impact with the horizontal stabilizer or fenestron tail rotor, and subsequent loss of control of the helicopter.
AD 2001-22-51 · published Dec 10, 2001, effective Dec 26, 2001
Agusta S.p.A. Model A119 Helicopters
This document publishes in the Federal Register an amendment adopting Airworthiness Directive (AD) 2001-22-51, which was sent previously to all known U.S. owners and operators of Agusta S.p.A. (Agusta) Model A119 helicopters by individual letters. This AD requires removing a certain part-numbered tail rotor blade (blade) on or before accumulating 50 hours time-in-service (TIS). This AD also requires visually or dye penetrant inspecting each blade at specified time intervals and removing any cracked blade before further flight. This AD is prompted by the discovery of a fatigue crack on a blade during an inspection. The actions specified by this AD are intended to prevent failure of a blade and subsequent loss of control of the helicopter.
AD 2001-25-02 · published Dec 11, 2001
Enstrom Helicopter Corporation Model TH-28 and 480 Helicopters
This amendment adopts a new airworthiness directive (AD) for Enstrom Helicopter Corporation (EHC) Model TH-28 and 480 helicopters. This AD requires establishing a life limit for certain upper and lower main rotor hub plates of 5000 hours time-in-service (TIS), creating a component history card or equivalent record, and replacing each main rotor hub plate (hub plate) having 5000 or more hours TIS with an airworthy hub plate. This AD is prompted by a recent reliability-based stress analysis that indicates a 5000-hour TIS life limit should be imposed on certain hub plates. The actions specified by this AD are intended to prevent failure of a hub plate, loss of control of the main rotor, and subsequent loss of control of the helicopter.
AD 81-18-01 R1 · published Dec 11, 2001
Bell Helicopter Textron, Inc. Model 206A, 206B, 206A-1, 206B-1, 206L, and 206L-1 Helicopters
This amendment revises an existing airworthiness directive (AD) for Bell Helicopter Textron, Inc. (BHTI) Model 206A, 206B, 206A-1, 206B-1, 206L, and 206L-1 helicopters that currently establishes a retirement life for the main rotor trunnion (trunnion) based on hours time-in-service (TIS). This amendment retains those requirements but revises the AD to remove the trunnion, part number (P/N) 206-011-120- 103, from the applicability. This amendment is prompted by the issuance of another AD for the BHTI Model 206L and 206L-1 helicopters that requires a different method of calculating the retirement life for the trunnions. The actions specified by this AD are intended to prevent failure of the trunnion due to fatigue cracks and subsequent loss of control of the helicopter.
AD 2001-25-08 · published Dec 18, 2001, effective Jan 2, 2002
Sikorsky Model S-70A and S-70C Helicopters
This amendment adopts a new airworthiness directive (AD) for Sikorsky Model S-70A and S-70C helicopters. This action requires certain inspections of each main landing gear drag beam (beam) for a crack and removing any cracked beam before further flight. This action also requires reducing the torque of the jackpad mounting bolt retention nut (nut) of each beam. This amendment is prompted by failure of a beam due to stress corrosion resulting from sustained tensile stress due partly to excessive torque of the nut. The actions specified in this AD are intended to prevent excessive torque of the nut, failure of a beam, and subsequent loss of control of the helicopter during takeoff or landing.
AD 2001-25-06 · published Dec 20, 2001, effective Jan 4, 2002
Sikorsky Aircraft Corporation Model S-76B and S-76C Helicopters
This amendment adopts a new airworthiness directive (AD) for Sikorsky Aircraft Corporation (Sikorsky) Model S-76B and S-76C helicopters. This action requires modifying the electrical power distribution system to change the source of the 28 volts supplied to Nos. 1 and 2 attitude and heading reference (AHRS) WARN circuits. This amendment is prompted by a ground test simulating loss of the essential bus by pulling both bus tie circuit breakers and switching off both batteries. As a result of this action, both autopilots went off-line. The actions specified in this AD are intended to prevent an AHRS fail signal to both autopilots due to a failure of the essential bus, loss of autopilot functions, and subsequent loss of control of the helicopter.
AD 2001-25-07 · published Dec 21, 2001, effective Jan 25, 2002
Eurocopter France Model AS 332C, L, L1, and L2 Helicopters
This amendment supersedes an existing airworthiness directive (AD) that applies to Eurocopter France Model AS 332C, L, L1, and L2 helicopters. That AD requires conducting a filter clogging warning test, and, if necessary, replacing a jammed valve with an airworthy valve. This amendment requires the same actions as the existing AD but references a revision to the previously referenced service information; adds fuel filter part numbers to the applicability; and clarifies other provisions throughout the AD. This amendment is prompted by jammed fuel filter by-pass valves. The actions specified by this AD are intended to prevent power loss due to fuel starvation, engine flameouts, and a subsequent forced landing.
AD 2001-24-12 · published Dec 4, 2001, effective Dec 19, 2001
Rolls-Royce Corporation (Formerly Allison Engine Company) 250-C20 Series Turboshaft and 250-B17 Series Turboprop Engines
This amendment supersedes an emergency airworthiness directive (AD) that was sent previously to all known U.S. owners and operators of Rolls-Royce Corporation (formerly Allison Engine Company) models 250- C20, -C20B, -C20F, -C20R, -C20R/1, -C20R/2, -C20S, and -C20W turboshaft engines, and 250-B17, -B17C, -B17D, -B17E, -B17F, -B17F/1, and -B17F/2 turboprop engines by individual letters. That action required replacement of any helical torquemeter gearshaft assembly with 100 hours or less time-since-new (TSN) with a serviceable helical torquemeter gearshaft assembly, before further flight. That amendment was prompted by a report of uncontained release of power turbine blades and disk fragments caused by engine overspeed, resulting in an uncommanded engine shutdown, engine fire, and damage to the aircraft. This amendment requires the same replacement, and adds engine model - 250-C20J to the applicability section of this AD. The actions specified by this AD are intended to prevent uncontained release of power turbine blades and disk fragments caused by engine overspeed, resulting in an uncommanded engine shutdown, engine fire, and damage to the aircraft.
AD 2001-25-04 · published Dec 19, 2001, effective Jan 23, 2002
Honeywell International Inc. Models LTS101-600A-2 and LTS101-600A-3 Turboshaft Engines; and LTP101-600A-1A and LTP101-700A-1A Turboprop Engines
This amendment adopts a new airworthiness directive (AD), that is applicable to Honeywell International Inc. (formerly AlliedSignal Inc. and Textron Lycoming) Models LTS101-600A-2 and LTS101-600A-3 turboshaft engines; and LTP101-600A-1A and LTP101-700A-1A turboprop engines. This amendment requires replacing certain fuel controls that have beryllium-copper bellows with improved fuel controls that incorporate Inconel 718 stainless steel welded bellows. This amendment is prompted by a report of an uncommanded power loss on a Textron Lycoming LTS101 engine due to a corrosion damaged fuel control bellows. The actions specified by this AD are intended to prevent the engine from reducing the fuel flow to minimum flow resulting in an uncommanded power loss.
AD 2001-25-05 · published Dec 19, 2001, effective Jan 23, 2002
Rolls-Royce Corporation (Formerly Allison Engine Company) AE 3007 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD), that is applicable to Rolls-Royce Corporation (formerly Allison Engine Company) AE 3007 series turbofan engines. That AD currently requires removal of certain compressor cone shafts from service before exceeding new cyclic life limits and replacement with serviceable parts. This amendment requires increasing the cyclic life limit for certain serial numbers of new compressor cone shafts, part number (P/N) 23070729, that are used on AE3007A1/3 and AE3007A1P engines. This amendment is prompted by recent approved changes in engineering and manufacturing processes for new compressor cone shafts P/N 23070729. The actions specified by this AD are intended to prevent low-cycle fatigue (LCF) failure of cone shafts, which could result in an uncontained engine failure and damage to the airplane.
AD 2001-26-06 · published Dec 21, 2001, effective Jan 7, 2002
CFE Company Model CFE738-1-1B Turbofan Engines
This amendment adopts a new airworthiness directive (AD) that is applicable to CFE Company model CFE738-1-1B turbofan engines. This action requires the removal of certain fan rotor disks from service. This amendment is prompted by a report from a forging manufacturer, of a metallurgical inclusion (contaminant) found in a forging made from a certain ingot of titanium. Fan rotor disks for model CFE738-1-1B engines have been manufactured from this same ingot and are suspect for metallurgical inclusions. The actions specified in this AD are intended to remove from service affected fan rotor disks, which if not removed, could result in uncontained engine failure and damage to the airplane.
AD 2001-26-11 · published Dec 31, 2001, effective Jan 30, 2002
Rolls-Royce, plc RB211 Trent 800 Series Turbofan Engines
This amendment supersedes an existing airworthiness directive (AD) that is applicable to Rolls-Royce, plc RB211 Trent 800 series turbofan engines. That AD currently requires initial and repetitive ultrasonic inspections of low pressure compressor (LPC) fan blade roots for cracks, and replacement, if necessary, with serviceable parts. This amendment requires initial inspections at modified thresholds and repetitive inspections at reduced intervals from the current AD using new LPC fan blade inspection criteria, and requires renewal of dry film lubricant on removed blades. This amendment is prompted by reports that an in-service engine experienced LPC fan blade root cracking at a lower life than previously forecast, and, the manufacturer's further investigation that has led to a better understanding of the causes of fan blade root cracking. The actions specified in this AD are intended to prevent LPC fan blade failure due to cracking, which could result in multiple fan blade release, uncontained engine failure, and possible damage to the airplane.
AD 2001-26-05 · published Dec 28, 2001, effective Jan 14, 2002
Hamilton Sundstrand Model 247F Propellers
This amendment adopts a new airworthiness directive (AD) that is applicable to certain Hamilton Sundstrand model 247F propellers. This action requires a one-time rework of certain model 247F propellers by removing all four propeller blades from service, replacing those blades with serviceable propeller blades, and marking the propeller with a new part number. This amendment is prompted by nine reports of the blades partially slipping at the bond joint between the blade tulip and the composite blade airfoil interface. The actions specified in this AD are intended to prevent the loss of a propeller blade, which may result in loss of airplane control.
AD 2001-23-17 · published Dec 3, 2001, effective Dec 28, 2001
GARMIN International GNS 430 Units
This amendment adopts a new airworthiness directive (AD) that applies to certain GARMIN International (GARMIN) GNS 430 units that are installed on aircraft. This AD requires you to modify the unit to incorporate circuitry changes to the GNS 430 unit's deviation and flag outputs. This AD is the result of reports of inaccurate course deviations caused by external electrical noise to the GNS 430 unit's course deviation indicator (CDI). The actions specified by this AD are intended to prevent such external noise from causing inaccurate course deviation displays in the GNS 430 unit's CDI or horizontal situation indicator (HSI). Such displays could result in the pilot making flight decisions that put the aircraft in unsafe flight conditions.
